Assembling titanium and steel parts by diffusion welding

ABSTRACT

A method of assembling together titanium parts and steel parts by diffusion welding, the method interposing two thin layers of niobium or vanadium and copper respectively between a titanium part and a steel part, evacuating the assembly of parts and interposed metal layers, and subjecting the assembly to hot isostatic compression at a temperature lying in a range 900° C. to 950° C. and at a pressure lying in a range 1000 bars to 1500 bars for about two hours. The method can be applied to fabricating turbine shafts for turbomachines.

The invention relates to a method of assembling together parts ofdifferent natures by diffusion welding, one of the parts being made oftitanium and the other of steel, and it also relates to metal partsobtained by the method, in particular turbine shafts for turbomachines.

In the context of research seeking to reduce the noise, the fuelconsumption, and the CO₂ emissions of airplane engines, the torquetransmitted by the low-pressure turbine shaft of a turbomachine has beenincreased very significantly, but without changing the diameter and theweight of the shaft, thereby leading the Applicant to investigate makinga shaft having a central portion of composite material with a titaniummatrix and including end pieces made of high-strength steel, which endpieces can be machined to have shapes that are relatively complex forconnection to other components of the turbomachine.

Assembling together the titanium central portion with the steelendpieces raises problems that have so far not yet been solved insatisfactory manner, particularly since the titanium-steel junctionsneed to present very strong mechanical characteristics for turbineshafts.

To this end, the invention provides a method of assembling togethertitanium parts and steel parts by diffusion welding, the method beingcharacterized in that it consists in:

interposing two thin metal layers between a titanium part and a steelpart, the two metal layers comprising a thin layer or foil of niobium orvanadium (beside the titanium) and a thin layer or foil of copper(beside the steel);

putting the assembly comprising the two parts and the two interposedmetal layers under a vacuum; and

subjecting said assembly to hot isostatic compression at a temperaturelying in the range 900° C. to 950° C., and at a pressure lying in therange 1000 bars to 1500 bars, the hot isostatic compression beingfollowed by controlled cooling.

Subjecting the assembly formed by the titanium part, the interposedmetal layers, and the steel part to hot isostatic compression serves toassemble together the titanium part and the steel part by diffusingwelding, the interposed metal layers preventing titanium migrating intothe steel and preventing iron from migrating into the titanium, sincethat would give rise to intermetallic phases weakening the junctionbetween the two parts.

In general, hot isostatic compression consists in making a stack ofelements, and in sealing the periphery of said elements, generally bywelding, while leaving an orifice leading to the interfaces fordegassing purposes. After degassing, performed by pumping out throughthe orifice, the orifice is closed in leaktight manner, in general bywelding. The stack is then subjected to a high pressure of a gas(generally argon) at a high temperature for a given duration. Hotisostatic compression eliminates clearances between the elements andachieves solid-state welding between the elements.

In the present invention, the duration of the hot isostatic compressionlies in the range one hour to three hours, approximately. It is abouttwo hours in a particular implementation of the invention, as describedbelow.

According to another characteristic of the invention, the methodconsists in subjecting the assembly to heat treatment including a firstdwell at about 800° C., followed by cooling, a second dwell at about450° C., and cooling.

The above-mentioned assembly is maintained at a pressure lying in therange 1000 bars to 1500 bars, approximately, during the heat treatment.

The interposed metal layers are of small thickness, lying in the range20 micrometers (μm) to 50 μm, approximately, and they may be formed bystamping foils or by depositing metal on the ends of the parts that areto be assembled together.

According to yet another characteristic of the invention, the methodconsists in machining the ends of the parts for assembling together inorder to give them non-plane complementary shapes, the end of the steelpart including at least one projecting portion engaged in an indentationin the titanium part.

These shapes take advantage of the thermal expansion difference betweentitanium and steel during hot isostatic compression to guarantee thatcontact is maintained between the two parts during heating and cooling.

The ends of the parts may be of a shape that is conical or biconical,for example.

The invention also provides a metal part comprising a titanium portionand a steel portion, the part being characterized in that these twoportions are assembled together by executing the diffusion weldingmethod as described above, the ends of said portions being united viathin interposed layers of niobium or vanadium (beside the titanium) andof copper (beside the steel).

According to another characteristic of the invention, the titaniumportion is a central portion having a steel portion assembled to eachend thereof by the above-specified diffusion welding method.

This metal part may be solid or tubular.

The central portion of this part may be made of a composite materialhaving a titanium matrix.

The metal part may constitute a turbine shaft for a turbomachine.

The invention also provides a turbomachine, such as a turbojet or aturboprop, characterized in that it includes a turbine shaft of theabove-defined type.

The invention can be better understood and other characteristics,details, and advantages thereof appear more clearly on reading thefollowing description made by way of example and with reference to theaccompanying drawings, in which:

FIG. 1 is a diagrammatic section view showing the junction of theinvention between a titanium part and a steel part;

FIG. 2 is a flow chart showing the essential steps of the method of theinvention;

FIG. 3 is a graph plotting pressure and temperature curves during thehot isostatic compression and the heat treatment in the method of theinvention;

FIG. 4 is a diagrammatic perspective view of another junction shapebetween a titanium part and a steel part;

FIG. 5 is a diagrammatic section view of the end of a steel part in avariant of the invention; and

FIG. 6 is a diagrammatic half-view in axial section of an end portion ofa turbine shaft of the invention.

FIG. 1 shows the assembly of a titanium part 10 with a steel part 12,the junction between these two parts being conical in shape and the endof the part 12 having an apex forming a rounded tip that is engaged in acavity of complementary shape in the end of the part 10.

The interface between the two parts is formed by a thin layer or foil 14of niobium or of vanadium, applied to the end of the titanium part 10,and a thin layer or foil 16 of copper applied to the end of the steelpart 12.

These interposed foils 14, 16 are of thickness lying for example in therange 20 μm to 50 μm, approximately, and they may be formed by stampingplane disks.

In a variant, the interposed layers may be formed directly on the endsof the titanium and steel parts, by depositing metal using a knownmethod, e.g. physical vapor deposition (PVD), chemical vapor deposition(CVD), or by electrolytic deposition.

The main steps of the method of the invention are shown diagrammaticallyin FIG. 2.

The parts for assembling are subjected in step 18 to careful cleaningand degreasing, and then in step 20 they are placed in a stainless steelcontainer or case of known type suitable for subsequently applying hotisostatic compression to the parts it contains.

A secondary vacuum is created in step 22 inside the container for abouttwelve hours, and then the container is closed in leaktight manner bywelding.

Thereafter, in a step 24, the container is placed in a hot isostaticcompression enclosure where the assembly comprising the titanium part,the interposed metal layers, and the steel part is subjected to hightemperature and pressure for a duration lying in the range one to threehours, approximately, the temperature lying in the range 900° C. to 950°C. and the pressure lying in the range 1000 bars to 1500 bars.

The assembly comprising the titanium part, the interposed metal layers,and the steel part is then subjected to heat treatment 26 in order toimprove the qualities of the steel, the heat treatment typicallycomprising a dwell at high temperature, e.g. about 800° C., followed bycontrolled cooling, and another dwell at high temperature, e.g. about450° C., followed by controlled cooling.

In a particular embodiment of the invention in which the part 10 is madeof Ti6242 titanium alloy and the part 12 is made of M250 maraging steel,the duration of the hot isostatic compression is two hours with thepressure being 1400 bars and the temperature being 925° C.

The first cooling is performed at a rate of 4° C. to 5° C. per minutedown to a temperature of about 400° C., and then the assemblyconstituted by the assembled parts 10 and 12 and the interposed metallayers is subjected to heat treatment including a dwell of two hours ata temperature of 790° C. and a dwell of two hours at a temperature of455° C., with controlled cooling after the first dwell and at a coolingrate of about 4° C. to 5° C. per minute down to ambient temperature. Thecooling after the dwell at 455° C. may be performed in air.

Preferably, the assembly comprising the two assembled-together partsremains subjected to the pressure of 1400 bars throughout the durationof the hot isostatic compression and the heat treatment of the steel.

The characteristics of hot isostatic compression and of the heattreatment of the steel are shown in FIG. 3, where curve P represents thevariation in the pressure applied to the parts for assembling together,and the curve T represents variation in the temperature to which thoseparts are subjected, with time in hours being marked along the abscissaaxis, and temperature in degrees C. and pressure in bars being marked upthe ordinate axis.

At a hydrostatic pressure in the range 1000 bars to 1500 bars, the hotisostatic compression serves to pass through the cooling step of theheat treatment without damaging the interposed metals. Damage to aductile metal such as copper is delayed under high hydrostatic pressuresince such pressure inhibits the formation of defects and inhibitsgrowth around such defects. This avoids the problems encountered in theprior art where the heat treatment of the steel gives rise to highlevels of shear in the interposed metal layers by an effect ofdifferential expansion under uniaxial pressure, and thus gives rise todestruction of the more ductile interposed metal.

FIG. 4 is a diagram showing a variant embodiment for the shape of thejunction between the titanium part 10 and the steel part 12. In thisvariant, the end of the steel part 12 includes a frustoconical tip withfluting 28 extending from the apex of the cone towards its base alonggenerator lines of the cone. The two parts 10 and 12 are also formedwith a central bore 30.

Another embodiment of the junction between the two parts is showndiagrammatically in FIG. 5, for the steel part 12.

The end of this part that is for assembly to the end of the titaniumpart, is of a biconical shape and comprises a frustoconical surface 32extending from the cylindrical periphery of the part 12 towards the axisof said part, and projecting from the part 12, this frustoconicalsurface being connected by a rounded convex edge 34 to a conical surface36 that extends in the direction opposite to the first conical surfaceand that forms an indentation in the end of the part 12, this surface 36extending from the rounded edge 34 to the central axis of the part 12.

The angle at the apex of the frustoconical surface 32 may be 120°, forexample, while the angle at the apex of the conical surface 36 is about160°.

The shape of the end of the titanium part 10 is complementary to theshape shown in FIG. 5.

FIG. 6 is a diagram showing a portion of a low-pressure turbine shaft ofthe invention, the shaft comprising a central portion 40 made of acomposite material having a titanium matrix, said central portion beingtubular about an axis 42 and being of greater thickness at its end 44for connection to the corresponding end 46 of a tubular endpiece 48 ofhigh strength steel that forms a link part linking to another componentof a turbomachine such as an airplane turboprop or turbojet.

Making the endpiece 48 out of steel makes it possible to impart anyappropriate shape thereto by machining, and its shape may be relativelycomplex.

The other end of the central portion 40 of the shaft (not shown) is alsoconnected to an endpiece of the same type as that shown in FIG. 6.

The connections between the ends 44 of the central portion 40 and theendpieces 48 are made by performing the above-described diffusionwelding method, using interposed niobium (or vanadium) and copperbetween the titanium and steel portions.

The junction 50 between each end of the central portion 40 and arespective endpiece 48 is of conical shape with a rounded apex forming acircular arc directed towards the central portion 40.

In an embodiment, the circular arc at the apex of the junction has aradius greater than 20 millimeters (mm) and the angle at the apex isabout 60°.

In a particular embodiment of the invention, the central portion 40 ofthe low-pressure turbine shaft has an outside diameter of 81 mm and ismade of a composite material having a Ti6242 matrix and long SiC fibers,and the endpieces 48 are made of an M250 maraging steel. The junctionsat the ends of the central portion 40 with the endpieces 48 are capableof transmitting a torque corresponding to the loss of a blade, i.e.about 70,000 newton-meters (Nm). Furthermore, these junctions arecapable of withstanding 25,000 takeoffs without cracks appearing, withthe torque transmitted during such takeoffs being of the order of 41,500Nm (where takeoff is the stage of flight during which the transmittedtorque is at a maximum under normal conditions of use).

1-15. (canceled)
 16. A method of assembling together titanium parts andsteel parts by diffusion welding, the method comprising: interposing twothin metal layers between a titanium part and a steel part, the twometal layers comprising a thin layer or foil of niobium or vanadium inaddition to the titanium and a thin layer or foil of copper in additionto the steel; putting the assembly comprising the two parts and the twointerposed metal layers under a vacuum; and subjecting the assembly tohot isostatic compression at a temperature lying in a range 900° C. to950° C., and at a pressure lying in a range 1000 bars to 1500 bars, thehot isostatic compression being followed by controlled cooling.
 17. Amethod according to claim 16, wherein a duration of the hot isostaticcompression lies in a range one hour to three hours, approximately. 18.A method according to claim 16, further comprising subjecting theassembly to heat treatment including a first dwell at about 800° C.,followed by cooling, a second dwell at about 450° C., and cooling.
 19. Amethod according to claim 18, further comprising maintaining theassembly at a pressure lying in a range 1000 bars to 1500 bars,approximately, during the heat treatment.
 20. A method according toclaim 16, wherein the interposed metals present a thickness lying in arange about 20 μm to about 50 μm.
 21. A method according to claim 16,further comprising machining ends of the parts for assembling togetherto give them non-plane complementary shapes, an end of the steel partincluding at least one projecting portion engaged in an indentation inthe titanium part.
 22. A method according to claim 21, furthercomprising giving a conical or a biconical shape to the ends of theparts.
 23. A method according to claim 16, wherein the interposed metalsare formed by depositing metal on the ends of the parts that are to beassembled.
 24. A method according to claim 16, further comprisingstamping the interposed metals to give them a shape corresponding to theshape of the ends of the parts.
 25. A metal part comprising: a titaniumportion; and a steel portion, the part being wherein the titanium andsteel portions are assembled together by executing diffusion weldingmethod according to claim 16, ends of the portions being united via thininterposed layers of niobium or vanadium in addition to the titanium andof copper in addition to the steel.
 26. A metal part according to claim25, wherein the titanium portion is a central portion having a steelportion assembled to each end thereof by the diffusion welding method.27. A metal part according to claim 26, that is tubular.
 28. A metalpart according to claim 27, wherein a central portion is made of atitanium-matrix composite material.
 29. A metal part according to claim28, constituting a turbine shaft for use in a turbomachine.
 30. Aturbomachine, a turbojet, or a turboprop, comprising a turbine shaftaccording to claim 29.